Method and Apparatus for Supplying Power to a Portable Electronic Device in an Aircraft

ABSTRACT

Provided is an apparatus. The apparatus includes a power conditioning module. The power conditioning module includes an input that is operable to receive a first power from an aircraft. The power conditioning module includes electronic circuitry that is operable to transform the first power to a second power. The second power is different from the first power and is suitable for charging a portable electronic device. The power conditioning module includes a status indication mechanism that is operable to indicate a status of the power conditioning module.

PRIORITY DATA

This application claims priority to application Ser. No. 13/224,111,filed on Sep. 1, 2011, entitled “METHOD AND APPARATUS FOR SUPPLYINGPOWER TO A PORTABLE ELECTRONIC DEVICE IN AN AIRCRAFT,” the disclosure ofwhich is incorporated herein by reference in its entirety.

TECHNICAL FIELD

The present disclosure generally relates to power regulation, and moreparticularly, to a voltage regulator that is operable to provide powerto portable electronic devices aboard an aircraft.

BACKGROUND

In the field of avionics, pilots have traditionally relied on flightbags to help them navigate the aircraft they operate. These flight bagsmay contain flight-related documents such as aircraft operation manuals,navigation charts, company policies, checklists, and information relatedto the trip, etc. The flight bags are typically heavy and may weigh asmuch as forty or fifty pounds. Such heavy weight of the flight bagsmakes them inconvenient for pilots or flight crew, who have to carrythese heavy bags with them to the cockpit of an aircraft on every tripthey take.

In recent years, the rapid advancement in computer and networkingtechnologies has led to the development of electronic flight bags (EFB).These electronic flight bags include electronic devices that store theinformation contained in a traditional flight bag in a digital format.However, to ensure the aircraft's operational safety, governmental rulesand regulations have placed stringent requirements on the electronicflight bags. For example, there are stringent requirements regarding theway in which power is supplied to an electronic flight bag. Existingelectronic flight bags have not adequately addressed these issues.

Therefore, while existing electronic flight bags have been generallyadequate for their intended purposes, they have not been entirelysatisfactory in every aspect.

SUMMARY

One of the broader forms of the present disclosure involves anapparatus. The apparatus includes a power conditioning module. The powerconditioning module includes: an input that is operable to receive afirst power from an aircraft; electronic circuitry that is operable totransform the first power to a second power, wherein the second power isdifferent from the first power and is suitable for charging a portableelectronic device; and a status indication mechanism that is operable toindicate a status of the power conditioning module.

Another one of the broader forms of the present disclosure involves amethod. The method includes: receiving, using a power conditioningmodule, a first power from an aircraft; converting, using the powerconditioning module, the first power to a second power, wherein thesecond power is different from the first power and is suitable forcharging a portable electronic device; monitoring a fault condition ofthe power conditioning module; and displaying the fault conditionthrough a light-emitting diode (LED) panel.

Yet another one of the broader forms of the present disclosure involvesa power conditioning system. The power conditioning system includes:input means for receiving a first power from an aircraft; electroniccircuitry means for transforming the first power to a second power,wherein the second power is different from the first power and issuitable for charging a portable electronic device; and display meansfor displaying a status of the power conditioning module.

BRIEF DESCRIPTION OF THE DRAWINGS

Aspects of the present disclosure are best understood from the followingdetailed description when read with the accompanying figures. It isemphasized that, in accordance with the standard practice in theindustry, various features are not drawn to scale. In fact, thedimensions of the various features may be arbitrarily increased orreduced for clarity of discussion. In the figures, elements having thesame designation have the same or similar functions.

FIG. 1 is a simplified block diagram of a power conditioning moduleaccording to various aspects of the present disclosure.

FIG. 2 is a simplified block diagram of electronic circuitry of thepower conditioning module according to various aspects of the presentdisclosure.

FIGS. 3-5 are circuit schematics of a power conditioning moduleaccording to an embodiment of the present disclosure.

FIG. 6 is a flowchart illustrating a method for conditioning a powerfrom an aircraft according to various aspects of the present disclosure.

DETAILED DESCRIPTION

It is to be understood that the following disclosure provides manydifferent embodiments, or examples, for implementing different featuresof the invention. Specific examples of components and arrangements aredescribed below to simplify the present disclosure. These are, ofcourse, merely examples and are not intended to be limiting. Variousfeatures may be arbitrarily drawn in different scales for simplicity andclarity.

Traditionally, flight crews have been carrying flight bags onboardaircrafts. These flight bags include flight-related documents such asflight manuals, company policies, checklists, and information related tothe trip, etc. The flight bags can be very heavy, which makes theirtransportation inconvenient and cumbersome for flight crews.

In recent years, electronic flight bags (EFB) have been proposed andimplemented to replace the traditional flight bags. These electronicflight bags include electronic devices that can digitally store theinformation contained in a traditional flight bag. Since a large amountof information can be stored in a relatively small electronic device,the electronic flight bags weigh much less than traditional flight bagscontaining paper documents. The elimination of the paper documents mayalso result in cost savings. In addition, it may be easier for anoperator to manage and manipulate flight information electronicallyusing the electronic flight bag.

To ensure the aircraft's operational safety, governmental rules andregulations have placed stringent requirements on various operationalaspects of electronic flight bags. One of these requirements deals withthe way in which power is supplied to an electronic flight bag. Forexample, the power supplied must be “clean” and free of spikes. This maynot be feasible for existing power supplies inside the cockpit, whichmay be generated by a motor. Depending on the speed, age, and health ofthe motor, or the serviceability of the interconnect wiring, the powerproduced by the motor may have significant variations and as such may betoo “dirty” to supply power to an electronic flight bag directly.

The present disclosure provides a power conditioning module that can beused to deliver power from an existing power source on an aircraft to aportable electronic device that can be used as an electronic flight bag.FIG. 1 is a simplified functional block diagram of the powerconditioning module 100 according to various aspects of the presentdisclosure. The power conditioning module 100 includes a printed circuitboard (PCB) assembly packaged with an enclosure. In other words, thepower conditioning module 100 may contain a PCB card.

In an embodiment, the power conditioning module 100 is operable toconvert an unregulated direct-current (DC) input voltage to a regulatedDC output voltage. In an embodiment, the unregulated DC input voltage isa voltage supplied by an existing power bus onboard an aircraft, whichmay be a 28 volt (V) nominal voltage. In operation, the 28V nominalvoltage may vary from about 27V to about 29V. In an embodiment, theregulated output voltage is about 5V, with current up to about 2.1amperes (A). The regulated output can then be used to supply power to aportable electronic device. In an embodiment, the portable electronicdevice is a computer tablet device. For example, the computer tabletdevice may be an Apple iPad® device serving as an electronic flight bag.It is understood, however, that other suitable personal electronicdevices may be powered up by the power conditioning module 100 inalternative embodiments.

Referring to FIG. 1, the power conditioning module 100 is coupled to a28V power source 110 and a 28V ground 120. The 28V power source 110provides the 28V DC power onboard an aircraft (e.g., inside the cockpitof the aircraft). The 28V ground provides a ground return for thatpower. As discussed above, this 28V power source may be dirty and mayhave significant voltage fluctuations or spikes. Thus, the powerconditioning module 100 is designed to have buffers and other interfacecircuitry that can handle these voltage fluctuations and spikes. In anembodiment, the power conditioning module 100 has an input tolerance ofabout 3%. The 28V supply 110 and the 28V ground 120 may be consideredinputs to the power conditioning module 100.

The power conditioning module 100 includes a switch 130. In anembodiment, the switch 130 is an external single-pole, double-throwmomentary. The switch 130 includes contacts that are normally open.Pushing the switch 130 to an “on” position commands the powerconditioning module 100 to turn on by connecting its center terminal toan on-wire. Pushing the switch 130 to the “off” position commands thepower conditioning module 100 to turn off by connecting its centerterminal to an off-wire. The switch 130 mechanically returns to a centerunconnected position when it is released. Latching the on/off state ofthe power conditioning module 100 is electronic internal to theregulator.

When a current output exceeds a predetermined threshold, for example2.1A, an over-current condition is created. When this happens, the powerconditioning module 100 is configured to automatically shut off theoutput voltage for an interval of time. In an embodiment, this intervalof time is about one second. Thereafter, the power conditioning module100 re-enables the output to again test for the over-current condition.The power conditioning module 100 may continuously repeat the cycledescribed above until the current output falls within the predeterminedthreshold, or until the power conditioning module 100 is turned off.

When a temperature exceeds a predetermined threshold, for example 140degrees Fahrenheit, an over-temperature condition is created. When thishappens, the power conditioning module 100 is configured to enter anover-temperature mode and shuts the output off. The power conditioningmodule 100 remains in the over-temperature mode until the temperaturefalls within the threshold temperature. In an embodiment, theover-temperature mode is cleared when the temperature is below 130degrees Fahrenheit.

The power conditioning module 100 is protected by a Ground-Fault CircuitInterrupters (GFCI) circuit feature internal to the power conditioningmodule 100. The power conditioning module measures a return current andcompares it to the output current to determine if there is a currentpath to vehicle ground. The power conditioning module 100 enters aground-fault mode if current leakage is found to exceed a predeterminedthreshold, for example in excess of about 500 milli-amperes (mA). Aftera ground-fault event has triggered, the power conditioning module 100electrically switches its output off until the power switch is operatedto cycle the power back on.

The power conditioning module 100 includes a status monitoring device150. The status monitoring device 150 is configured and operable tomonitor the status of the power conditioning module 100. In anembodiment, the status monitoring device 150 includes a light-emittingdiode (LED) module 160. The LED module 160 includes an LED panelcontaining a plurality of LED indicators of different colors, each oneof which is illuminated to indicate a particular condition. Theenclosure of the power conditioning module 100 may include a light pipeto conduct the LED light to the outside of the enclosure. The operationof the LED indicators is exclusive in that there may only be one LEDindicator active at a time.

In an embodiment, the LED module 160 includes a green LED indicator, ayellow LED indicator, and a red LED indicator. The green LED indicatorilluminates when the power conditioning module 100 senses a steady 28VDC input and is powered on with no over-current, over-temperature, orground-fault situations; and detects a suitable load on the circuit fromthe Electronic flight bag device. In other words, the power conditioningmodule 100 is functioning properly as desired. The yellow LED indicatorilluminates when the power conditioning module detects anover-temperature or over-current situation. The red LED indicatorilluminates when the power conditioning module detects a ground-faultsituation.

The power conditioning module 100 includes a detect pin 200. The detectpin 200 is configured to identify itself to the portable electronicdevice attached thereto. In an embodiment where the portable electronicdevice is an iPad, the detect pin 200 is operable to identify the powerconditioning module as a power accessory to the iPad.

The power conditioning module 100 includes a Universal Serial Bus (USB)Data+ pin 210 and an USB Data− pin 220. The USB Data+pin 210 and the USBData− pin 220 each have an USB interface and serve as data pins herein.The USB Data+pin 210 and the USB Data− pin 220 are configured to givefeedback to the power conditioning module 100 such that the powerconditioning module 100 cannot be turned on and energized if there is noload (i.e., the portable electronic device) present. In otherembodiments, it is contemplated that these data pins may havealternative communication interfaces different from USB.

The power conditioning module 100 includes an USB 5V data output pin 230and an USB ground pin 240. The USB 5V data output pin 230 is configuredto deliver a steady clean supply voltage (e.g., free of fluctuations orspikes) to the portable electronic device attached thereto. Stateddifferently, the USB 5V data output pin 230 provides a charging voltage.In an embodiment, the voltage delivered is within 3% of 5V (4.85V to5.15V). The USB ground pin 240 serves as electrical ground for the poweroutput pin 230. In other embodiments, it is contemplated that the pins230 and 240 may have alternative communication interfaces different fromUSB.

According to an embodiment, the following procedure may be employed tooperate the power conditioning module 100. First, a 28V power isprovided to the power conditioning module 100 through the 28V supply110. Momentary contact of the on switch 130 initiates a sequence thattests for acceptable conditions, then applies a 5V power to the USB 5Voutput pin 230 if conditions are within predetermined limits. Thesefollowing conditions must be met:

-   -   1. The detect pin 200 must be grounded by the attachment of the        portable electronic device attached thereto.    -   2. Temperature must be below 140 degrees Fahrenheit.

After powering on, the current must remain below 2.3 A, and the currentdifference between the two terminals must remain below 500 mA. Ifcurrent exceeds the limit, this condition is latched as a current fault.The 5V output is disabled for approximately one second, and is thenre-enabled. If the current is still over limit, then the board continuesto cycle off, testing the current until the current detected isconsistently less than the limit.

If the current difference between the USB 5V output pin 230 and the USBground pin 240 is greater than 500 mA, then a Ground Fault Interrupter(GFI) condition is latched. In an embodiment, this condition can becleared by removing the 28V power from the input. In other embodiments,this condition may be cleared by operating the switch off and then backon.

During the operation of the power conditioning module 100, the green LEDindicator is illuminated if the following conditions are met:

-   -   Adequate power is provided from the input (e.g., from the 28V        supply 110)    -   A suitable load is detected on the output (e.g., a functioning        Apple iPad device)    -   No over-temperature condition is detected (e.g., temperature        should be kept under 140 degrees Fahrenheit)    -   No over-current condition is detected    -   No under-current condition is detected    -   No over-voltage condition is detected    -   No under-voltage condition is detected    -   No GFI condition is detected

Thus, the illumination of the green LED indicator means that everythingis working properly, and no operator action needs to be taken. One theother hand, the yellow LED indicator is illuminated if anover-temperature condition is detected, or if an over/undercurrent/voltage condition is detected. The presence of these conditionsmeans that the power conditioning module 100 is not functioningproperly, and that the operator needs to take actions to ensure thepower conditioning module 100 returns to a fully functional state.

Lastly, the red LED indicator is illuminated when a GFI condition isdetected. The GFI condition is considered an absolute hard fault. Forexample, it may indicate that there is a direct short circuit to theaircraft frame's ground, which presents a threat to the airplane, thecrew, and the passengers. The GFI fault is not momentarily resettable.The GFI condition shuts down the power conditioning module. The powerconditioning module cannot be powered back on until the load device isdisengaged, the power conditioning module 100 is turned off, and the GFIfault is cleared. Afterwards, the load is re-engaged, and the powerconditioning module 100 is turned on again.

The enclosure of the power conditioning module may have more than oneform factor. In one embodiment, the form factor of the enclosure is abox-enclosed mount with a D subconnector on the side. It is apermanently mounted piece of avionics on the aircraft. In this case, thepower conditioning module (including the enclosure) itself and itsinstallation on the aircraft have to be approved by the necessarygovernmental agencies such as the Federal Aviation Administration (FAA).

In another embodiment, the form factor of the enclosure is a portabledongle. Out of one side is a coil cable that goes to a 3-pin circularconnector that can be connected to a cabin cockpit bulkhead connector inthe side wall, and the other side of the enclosure has a connectorconfigured to be coupled to the portable electronic device. In theembodiment where the portable electronic device is the Apple iPad, theconnector coming out of the enclosure is a 30-pin connector configuredto be coupled to the iPad. The portable dongle form factor allows thepower conditioning module 100 to be transported from aircraft toaircraft.

The power conditioning module 100 contains circuitry 300 that isimplemented within either of the enclosure form factors discussed above.The circuitry 300 may be implemented on a PCB board or a card. Thecircuitry 300 is designed and implemented to carry out the variousfunctionalities of the power conditioning module 100 discussed above. Itis understood, however, that the circuitry 300 may overlap with thevarious components 110-240 described above in association with FIG. 1.That is, one or more of these components 110-240 may be implemented atleast partially within the circuitry 300 in some embodiments, and thatthe circuitry 300 and the components 110-240 are not mutually exclusiveof one another.

A simplified functional block diagram of the circuitry 300 is shown inFIG. 2. The circuitry 300 includes blocks 310-410, wherein each blockmay include one or more circuit components (or electronic devices), forexample transistors, resistors, capacitors, inductors, diodes,transformers, fuses, etc. The functionalities of each of these blocks310-410 are discussed below in more detail.

The block 310 is a 28V input block. The block 310 contains electroniccircuitry that interfaces with an input power (voltage) received from anaircraft. Typically, the power generated and available from an aircraftis not steady or clean enough to be used to power an electronic deviceto be used as an electronic flight bag. For example, for many commercialplanes, though they may be designed to provide a 28V voltage output,their actual voltage output may vary from about 22V to about 32V. Thisvoltage output may be accompanied by frequent voltage bursts as well.Thus, to handle this dirty voltage, the block 310 may contains voltagebuffers and other interfacing circuitry that minimizes the adverseimpacts of the voltage fluctuations and spikes.

The block 320 is an input voltage range power-on reset block. The block320 contains electronic circuitry that monitors the input power andprovides a notification to a user or operator in case the input powerbehaves irregularly. For example, the block 320 may be operable tomonitor the input power (e.g., voltage from the aircraft) and determinewhether it is within a predetermined threshold range. If the input powerfalls outside this predetermined threshold range, then the block 320 maynotify the user that the input power has exceeded the threshold, and mayrequire the user to take action to address this problem, for exampleshutting down the output and reinitializing the load.

The block 330 is an on/off latch block. In one embodiment, the block 330contains a handheld switch mechanism. In another embodiment, the block330 contains an external illuminated switch enunciator mechanism. It isunderstood that the handheld switch mechanism and the switch enunciatormechanism may each be implemented outside the circuitry 300 asphysically separate devices. The block 330 includes a momentary-on, amomentary-reset and a momentary-off. Momentary-on and momentary-resetmay be accomplished by pushing the switch to a forward position.Momentary-off is accomplished by bringing the switch back to a middleposition. The block 330 includes one or more common anodes that areoperable to sense the momentary switching of the switch (or switchcommand) and latches (or holds) the command.

The block 340 corresponds to an on/off switch. In one embodiment, theswitch is implemented outside the circuitry 300. If a box form factor isused for the power conditioning module, there is a switch enunciator onthe panel, the switch enunciator is a logic switch and contains logiccircuitry and LED devices. The illumination of the LED devices informsthe operator or user of the system's status. For example, if the LEDdevices illuminate a red light, then that indicates a hard fail orfault. If the LED devices illuminate a yellow or amber light, then thatindicates a resettable fail. If the handheld form factor is used for thepower conditioning module, then the switch is a mechanical switch. It'sa momentary normally open double-pole-double-throw switch.

The block 350 is a local 5V regulator block. This block provides powerfor the board. The block 350 regulates power for the components on thepower conditioning module.

The block 360 is a 5V regulator block. If all the interlocks are met bythe board and the load device and the input power, then the block 360allows the user to enable the output.

The block 370 is a 5V output block. The block 370 outputs a steady 5V DCvoltage output. The block 370 includes sense elements for sensing the 5VDC output and a 2.1 A current output with a predetermined variance. Ifthe voltage or current output is outside a predetermined range (forexample, greater than 3% of 2.1 A for the current output), then theoutput will not be allowed to go out.

The block 380 is an over-temperature block. The block 380 is forhandling the over-temperature condition of the power conditioning moduleitself. If heat is being dissipated too quickly, or not quickly enoughso that the device is getting overheated, it will shut the device downas opposed to the output. Thus, it protects the aircraft wiring.

The block 390 is a one-shot/over-current block. When the output isapplied, there is an associated voltage drop once power is applied. Theblock 390 ensures that there is enough off board voltage to keep it fromcycling on and off. The block 390 offers the ability to keep powersteady long enough to stabilize the output once the output power isapplied. In this manner, the power conditioning module will notautomatically shut down.

The block 400 is a GFI latch/GFI fault block. A GFI fault is a hardfailure, which will shut down the device and gives a red LED indication.The GFI fault requires the user to disconnect the load and reconnect theload before the device is turned back on.

The block 410 is an electronic device detect block. The block 410 sensesthe load device. If there is no load present, then it will not allowpower to be applied through the output. The block 410 ensures that therewould not be a plug floating in the cockpit of an aircraft with power onit. In an embodiment, the block 410 is designed and configured to sensean Apple iPad device as a load device.

FIGS. 3A-3D, FIGS. 4A-4C, and FIGS. 5A-5D are circuit schematic drawingsof the power conditioning module 100 according to an embodiment. Thepower conditioning module 100 provides an indication and a shunt in theevent of an error in an aviation application. As discussed before, theembodiment of the power conditioning module implemented according to thecircuit schematics shown in FIGS. 3-5 is configured to clean up a dirtyexisting power supply from an aircraft and convert this power to asteady power that can be used to charge a portable electronic devicesuch as an Apple iPad device, which can be used as an electronic flightbag. The voltage supplied by the power conditioning module issubstantially free of voltage fluctuations or spikes. The powerconditioning module accounts for over-voltage, under-voltage,over-current, and under-current situations, as well as thermalconditions on the circuit that can lead to thermal runaway situations.The existence or triggering of these conditions may be communicated toan operator through an LED panel that is implemented on the powerconditioning module. The LED panel may illuminate different colors oflight depending on the fault conditions. In the embodiment illustratedin FIGS. 3-5, the components of the power conditioning module areimplemented using physical hardware devices (as opposed to softwarecode). The power conditioning module 100 meets the stringent standardsset forth by government rules and regulations regarding theairworthiness of a power conditioning module that is qualified to beused in an aircraft.

FIG. 6 is a flowchart illustrating a method 600 of conditioning a powerfrom an aircraft according to various aspects of the present disclosure.The method 600 includes step 610 in which a power conditioning module isused to receive a first power from an aircraft. The method 600 includessteps 620 in which the power conditioning module is used to convert thefirst power into a second power. The second power is different from thefirst power and is suitable for charging a portable electronic device.The portable electronic device may be a computer tablet device, forexample an Apple iPad device. The method 600 includes steps 630 in whicha fault condition of the power conditioning module is monitored. Themethod 600 includes step 640 in which the fault condition is displayedthrough a light-emitting diode (LED) panel. It is understood thatadditional steps may be performed before, during, or after the steps610-640 of FIG. 6. For example, the method 600 may include using thepower conditioning module to charge the portable electronic device.

The foregoing has outlined features of several embodiments so that thoseskilled in the art may better understand the detailed description thatfollows. Those skilled in the art should appreciate that they mayreadily use the present disclosure as a basis for designing or modifyingother processes and structures for carrying out the same purposes and/orachieving the same advantages of the embodiments introduced herein.Those skilled in the art should also realize that such equivalentconstructions do not depart from the spirit and scope of the presentdisclosure, and that they may make various changes, substitutions andalterations herein without departing from the spirit and scope of thepresent disclosure.

1. A power conditioning module for interfacing with an avionics machineand a portable electronic flight bag, comprising: electrical circuitryelectrically coupled to the avionics machine, the electrical circuitrydrawing dirty electrical energy from an electrical energy supply of theavionics machine, wherein the electrical circuitry contains a pluralityof microelectronic circuit components configured to: convert the dirtyelectrical energy to a clean electrical energy; detect anabnormal-current fault condition; detect an abnormal-temperature faultcondition; and detect a ground fault circuit interrupt (GFCI) faultcondition indicative of a potential electrical short circuit that is athreat to the avionics machine; and a status monitoring deviceelectrically coupled to the electrical circuitry, wherein the statusmonitoring device is configured to communicate, to a user, a pluralityof at least three different statuses of the power conditioning module inresponse to the electrical circuitry's detection of the abnormal-currentfault condition, the abnormal-temperature fault condition, the GCI faultcondition, or absence of any fault conditions; wherein the powerconditioning module is configured to deliver the clean electrical energyto the portable electronic flight bag.
 2. The power conditioning moduleof claim 1, wherein the power conditioning module is non-portablymounted to the avionics machine.
 3. The power conditioning module ofclaim 1, wherein the power conditioning module is a portable dongle thatcan be transported from the avionics machine to another avionicsmachine.
 4. The power conditioning module of claim 1, wherein the statusmonitoring device includes a light-emitting diode (LED) modulecontaining LEDs of different colors, and wherein each color correspondsto a detection of one of: a specific fault condition and the absence ofany fault conditions.
 5. The power conditioning module of claim 1,further comprising: a detect pin that is electrically coupled to theelectrical circuitry and configured to identify the power conditioningmodule as a power accessory to the electronic flight bag attachedthereto.
 6. The power conditioning module of claim 1, furthercomprising: one or more data pins configured to prevent the powerconditioning module from being turned on when no electronic flight bagis coupled to the power conditioning module.
 7. The power conditioningmodule of claim 1, further comprising: one or more output pins throughwhich the clean electrical energy is delivered to the electronic flightbag.
 8. The power conditioning module of claim 1, wherein: the dirtyelectrical energy includes a 28 volt electrical voltage that containsvoltage spikes; and the clean electrical energy includes a 5 voltelectrical voltage that is substantially free of voltage spikes.
 9. Thepower conditioning module of claim 1, wherein the electronic flight bagincludes a computer tablet.
 10. The power conditioning module of claim1, wherein the avionics machine includes an airplane. 11-30. (canceled)